FOUND SUPPLEMENT M400-S08 Transport Canada Approved Flight Manual Supplement For WIPLINE MODEL 3450 SEAPLANE FLOATS This supplemental manual is applicable to Wipline Model 3450 seaplane float equipped airplanes or Wipline Model 3450 seaplane float equipped FBA- 2C1 airplanes with Mod 1043 installed. Mod 1043 replaces the plain flap system on the model FBA-2C1 airplane with a slotted Fowler-type flap system (commonly referred to as Fowler Flaps ). Therefore where 2C2 is used in this manual it is acceptable to read 2C1 with Mod 1043 installed. This Supplement must be attached to the Transport Canada Approved Airplane Flight Manual when the airplane is modified by the installation of Wipline Model 3450 seaplane floats in accordance with Found Aircraft Canada drawing D257 Issue 2 or later approved revision. The information contained herein supplements or supersedes the basic flight manual, airplane markings and/or placards only in those areas listed herein. For Limitations, Procedures, and Performance information not contained in this Supplement, consult the airplane markings and placards and/or basic Airplane Flight Manual, (P/N: FAC2-M400). P/N M400-S08 ISSUE 1 1 OF 38
SUPPLEMENT M400-S08 FOUND LOG OF REVISIONS Rev. No. Approved Date (Original) Name 2 OF 38 ISSUE 1
FOUND SUPPLEMENT M400-S08 LIST OF EFFECTIVE PAGES Page Date Page Date 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 ISSUE 1 3 OF 38
SUPPLEMENT M400-S08 FOUND TABLE OF CONTENTS TITLE PAGE LOG OF REVISIONS... 2 LIST OF EFFECTIVE PAGES... 3 SECTION 1: GENERAL... 7 INTRODUCTION... 7 DESCRIPTIVE DATA... 9 SECTION 2: LIMITATIONS... 10 INTRODUCTION... 10 AIRSPEED LIMITATIONS... 10 WEIGHT LIMITS... 11 CENTER-OF-GRAVITY LIMITS... 11 OTHER LIMITATIONS... 11 PLACARDS... 12 SECTION 3: EMERGENCY PROCEDURES... 13 INTRODUCTION... 13 AIRSPEEDS FOR EMERGENCY OPERATION... 13 EMERGENCY PROCEDURES CHECKLISTS... 14 ENGINE FAILURES... 14 FORCED LANDINGS... 14 SECTION 4: NORMAL PROCEDURES... 16 AIRSPEEDS FOR NORMAL OPERATION... 16 NORMAL PROCEDURES CHECKLISTS... 17 PREFLIGHT INSPECTION... 17 TAKEOFF... 18 ENROUTE CLIMB... 18 AFTER LANDING... 19 SECURING AIRPLANE... 19 AMPLIFIED NORMAL PROCEDURES... 20 TAXIING... 20 CROSSWIND OPERATIONS... 20 TAKEOFF... 21 4 OF 38 ISSUE 1
FOUND SUPPLEMENT M400-S08 LANDING... 22 GLASSY WATER LANDING... 22 CROSSWIND LANDING... 22 SECTION 5: PERFORMANCE... 23 HEIGHT LOSS IN STALLS... 23 AIRSPEED CALIBRATION... 24 STALL SPEED... 25 BEST ANGLE-OF-CLIMB... 26 BEST RATE-OF-CLIMB... 27 TIME, FUEL AND DISTANCE TO CLIMB... 28 SECTION 6: WEIGHT AND BALANCE... 29 FLOAT BAGGAGE COMPARTMENTS... 29 FLOATPLANE REFERENCE DATUM... 29 FLOATPLANE WEIGHING PROCEDURES... 30 FLOATPLANE WEIGHT AND BALANCE PROCEDURES... 33 CENTER OF GRAVITY MOMENT ENVENLOPE... 35 CENTER OF GRAVITY RANGE ENVENLOPE... 36 SECTION 7: AIRPLANE AND SYSTEMS DESCRIPTION... 37 FOUND AIRCRAFT CANADA MODIFICATIONS... 37 WATER RUDDER SYSTEM... 37 ISSUE 1 5 OF 38
SUPPLEMENT M400-S08 FOUND INTENTIONALLY LEFT BLANK 6 OF 38 ISSUE 1
FOUND SUPPLEMENT M400-S08 SECTION 1 GENERAL INTRODUCTION This supplemental manual is applicable to Wipline Model 3450 seaplane float equipped airplanes or Wipline Model 3450 seaplane float equipped FBA- 2C1 airplanes with Mod 1043 installed. Mod 1043 replaces the plain flap system on the model FBA-2C1 airplane with a slotted Fowler-type flap system (commonly referred to as Fowler Flaps ). Therefore where 2C2 is used in this manual it is acceptable to read 2C1 with Mod 1043 installed. This supplement provides information and limitations not included in the Transport Canada approved markings and placards, and/or Airplane Flight Manual (P/N: FAC2-M400). The aircraft is to be operated under the NORMAL CATEGORY only. ISSUE 1 7 OF 38
SUPPLEMENT M400-S08 FOUND WING AREA 180 SQ-FT Figure 1 Three View - Normal Ground Attitude 8 OF 38 ISSUE 1
FOUND SUPPLEMENT M400-S08 DESCRIPTIVE DATA MAXIMUM CERTIFICATED WEIGHTS Maximum Operational Weight: Takeoff: 3700 lbs Landing: 3700 lbs Maximum Weights in Baggage Compartment: Main Baggage Area 250 lbs maximum STANDARD AIRPLANE WEIGHTS Standard Empty Weight: 2360 lbs * Maximum Useful Load: 1340 lbs * * the above weights may vary depending on configuration. SPECIFIC LOADINGS Wing Loading: 20.6 lbs/sq.ft. Power Loading: 12.3 lbs/hp ISSUE 1 9 OF 38
SUPPLEMENT M400-S08 FOUND SECTION 2 LIMITATIONS INTRODUCTION The Bush Hawk-XP Wipline seaplane must be operated in accordance with the limitations contained in this section. These include operating limitations, instrument markings, colour coding and basic placards, powerplant, systems and equipment limitations. The limitations shown in this section apply only to operations of the Bush Hawk-XP equipped with Wipline Model 3450 seaplane floats. AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown below: SPEED KCAS KIAS REMARKS V A Maneuvering Speed 117 118 Do not make full or abrupt control movements above this speed. NOTE The operating speeds for the float installation are unchanged from the landplane operating airspeeds except for the indicated stall speeds. The airspeed indicator markings remain unchanged from the landplane as the floatplane stall speeds are more conservative than the landplane stall speeds. 10 OF 38 DOT APPROVED ISSUE 1
FOUND SUPPLEMENT M400-S08 WEIGHT LIMITS Maximum Takeoff Weight: 3700 lbs. Maximum Landing Weight: 3700 lbs. Maximum Weight in Baggage Compartment 250 lbs. (Arm = 94 ) Maximum Weight in Float Baggage Compartments 50 lbs. each (Arm = -4 ) CENTER-OF-GRAVITY LIMITS Center-of-Gravity Range: Forward: Aft: Reference Datum: 17.0 inches aft of datum at 2750 lbs or less. 20.5 inches aft of datum at 3700 lbs max. GW with linear variation with weight in between. 23.5 inches aft of datum at all weights. Lower forward corner of the front door OTHER LIMITATIONS FLAP LIMITATIONS Approved Takeoff Range:... 0 o to 20 o Approved Landing Range:... 0 o to 30 o WATER RUDDER LIMITATIONS Water rudders must be retracted for all flight operations. ISSUE 1 DOT APPROVED 11 OF 38
SUPPLEMENT M400-S08 FOUND PLACARDS The following information is displayed in the form of composite or individual placards. 1. Above the airspeed indicator: MANEUVER SPEED = 118 KIAS 2. Located on the centre instrument panel below the throttle control FOR AIRCRAFT EQUIPPED WITH WIPLINE MODEL 3450 FLOATS, MAX GROSS = 3700 LBS. REFER TO FMS M400-S08 12 OF 38 DOT APPROVED ISSUE 1
FOUND SUPPLEMENT M400-S08 SECTION 3 EMERGENCY PROCEDURES NOTE These items supplement the emergency procedures. Be sure to follow the procedures in Flight Manual P/N FAC2-M400 except as noted below. INTRODUCTION This section provides the operational checklists that are specific to with Wipline Model 3450 seaplane floats in abnormal circumstances and emergencies that may occur on the water or during flight. Only the sections that are affected by the Wipline floats are included in this supplement. Emergency landings on water should be done with water rudders up, aircraft should be established in a normal water landing attitude with the tail slightly low. On touchdown on the water, gently pull the elevator back to the full up position allowing the floatplane to come off the step and decelerate. If damage occurs to the floats causing compartments to flood, open doors, get life vest on, and taxi aircraft to shallow water as quickly as possible. Emergency landings on land should be done with water rudders up, aircraft in a normal landing attitude on touchdown, and the control wheel full aft after contact. AIRSPEEDS FOR EMERGENCY OPERATION Engine Failure after Takeoff Wing Flaps - Up... 80 KIAS Wing Flaps - 10 o... 75 KIAS Wing Flaps - 20 o... 70 KIAS Maneuvering Speed...118 KIAS Maximum Glide (Flaps - Up)... 75 KIAS Precautionary Landing With Engine Power Wing Flaps - Up... 80 KIAS Wing Flaps - 30 o... 70 KIAS Landing Without Engine Power Wing Flaps - Up... 80 KIAS Wing Flaps - 30 o... 70 KIAS ISSUE 1 13 OF 38
SUPPLEMENT M400-S08 FOUND EMERGENCY PROCEDURES CHECKLISTS ENGINE FAILURES ENGINE FAILURE DURING TAKEOFF RUN 1. Throttle... IDLE 2. Control Wheel... FULL AFT. 3. Flaps... RETRACT 4. Mixture... IDLE CUT OFF. 5. Ignition Switch... OFF 6. Master Switch... OFF 7. Alternator Switch... OFF ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF 1. Land... LAND or WATER (Straight ahead turning only to avoid obstacles) 2. Airspeed... 80 KIAS (Flaps UP) 70 KIAS (Flaps 20 ) If time permits: 3. Mixture... IDLE CUT-OFF 4. Fuel Shutoff Valve... OFF 5. Ignition Switch... OFF 6. Master Switch... OFF 7. Alternator Switch... OFF 8. Flaps... AS REQUIRED FORCED LANDINGS EMERGENCY LANDING ON WATER WITHOUT ENGINE POWER 1. Seats... SECURE 2. Seat belts... FASTENED 3. Loose Articles... SECURE 4. Airspeed... 80KIAS (Flaps UP) 70 KIAS (Flaps 30 o ) 14 OF 38 DOT APPROVED ISSUE 1
FOUND SUPPLEMENT M400-S08 Before touchdown: 5. Doors... UNLATCH PRIOR TO TOUCHDOWN 6. Mixture... IDLE CUT-OFF 7. Auxiliary Fuel Pump Switch... OFF 8. Fuel Shutoff Valve... OFF 9. Ignition Switch... OFF 10. Water Rudders... UP 11. Master Switch... OFF 12. Alternator Switch... OFF 13. Touchdown... SLIGHTLY TAIL LOW 14. Control Wheel... HOLD FULL AFT PRECAUTIONARY LANDING WITH ENGINE POWER 1. Seats... SECURE 2. Seat Belts... FASTENED 3. Loose Articles... SECURE 4. Airspeed... 80 KIAS Minimum 5. Wing Flaps... UP 6. Selected Field... FLY OVER Note terrain and obstructions. 7. Radio & Electrical Switches... OFF 8. Wing Flaps... 10~20 o (or 30 o for steep approach) 9. Airspeed... 75 KIAS (Flaps 10 o ) 70 KIAS (Flaps 30 o ) 11. Propeller... HIGH RPM 12. Doors... UNLATCH PRIOR TO TOUCHDOWN After touchdown: 10. Ignition Switch... OFF 11. Master Switch... OFF 12. Alternator... OFF ISSUE 1 DOT APPROVED 15 OF 38
SUPPLEMENT M400-S08 FOUND SECTION 4 NORMAL PROCEDURES NOTE These items supplement the normal procedures. Be sure to follow the procedures in Flight Manual P/N FAC2-M400 except as noted below. AIRSPEEDS FOR NORMAL OPERATION Unless otherwise noted, the following airspeeds are based on a maximum weight of 3700lb. and may be used at a lesser weight. CONDITION TAKEOFF Normal Climb Out Short Field Takeoff - Flaps 15 deg, Speed at 50 feet Short Field Takeoff Flaps 20 deg, Speed at 50 feet ENROUTE CLIMB, FLAPS UP Normal - Sea Level Best Rate of Climb - Sea Level Best Angle of Climb - Sea Level KIAS 70-80 67 65 75-85 79 65 LANDING APPROACH Normal Approach - Flaps Up Normal Approach - Flaps 30 deg Short Field Approach - Flaps 30 deg 80-90 65-75 66 BALKED LANDING Maximum Power - Flaps 30 deg 80 MAXIMUM RECOMMENDED TURBULENT AIR PENETRATION SPEED 118 MAXIMUM DEMONSTRATED CROSSWIND VELOCITY Takeoff or Landing 15 16 OF 38 DOT APPROVED ISSUE 1
FOUND SUPPLEMENT M400-S08 NORMAL PROCEDURES CHECKLISTS PREFLIGHT INSPECTION BEFORE ENTERING FLOATPLANE 1. Floatplane Approved Flight Manual Supplement with Airplane Flight Manual should be available in the airplane. 2. Floats, Struts, and Float Fairings... INSPECT for dents, cracks, etc. 3. Float Compartments... INSPECT for water accumulation. 4. Pump out each float compartment. Ensure the rubber stoppers are replaced after pumping and they are seated with a snug fit. Inspect the floats for leaks if there appears to be an excess amount of water in any of the compartments. If there is red hydraulic fluid in any water, investigate fittings and lines in that bay before proceeding. 5. Water Rudders... CHECK actuation cables PRIOR TO ENGINE START 1. Water Rudder Operation... CHECK VISUALLY 2. Water Rudders... DOWN for taxing on water (lever full forward) 3. Water Rudders... CHECK freedom of movement and security ISSUE 1 DOT APPROVED 17 OF 38
SUPPLEMENT M400-S08 FOUND TAKEOFF NORMAL TAKEOFF 1. Doors... CLOSED, UNLOCKED 2. Water Rudders... UP (retraction lever full aft) 3. Wing Flaps... 10~20 deg (20 deg recommended) 4. Control Wheel... HOLD FULL AFT 5. Pitch Trim... SET to NEUTRAL 6. Power... FULL THROTTLE at 2700 RPM 7. Mixture... RICH 8. Elevator Control... MOVE FORWARD gently when the nose pitches up and stops rising to attain planing attitude. APPLY LIGHT BACK PRESSURE to lift off at airspeed of 60-65 KIAS. 9. Wing Flaps... UP at Safe Speed and altitude 10. Climb Speed... 75-85 KIAS NOTE To reduce takeoff water run, the technique of raising one float out of the water may be used. NOTE If the flap indicator is non-functional, for example, flap indicator reads zero when flaps are deployed, use flaps up for all takeoffs. ENROUTE CLIMB 1. Airspeed... 75-85 KIAS 2. Power... FULL THROTTLE at 2600 RPM 3. Mixture... RICH (Above 3000ft, LEAN as required) 4. Auxiliary Fuel Pump... OFF 18 OF 38 DOT APPROVED ISSUE 1
FOUND SUPPLEMENT M400-S08 BEFORE LANDING 1. Water Rudders... UP 2. Wing Flaps... AS DESIRED (30 deg for short approach) 3. Airspeed (Flaps Up)... 80-90 KIAS @ 3700 lb 4. Airspeed (Full Flap)... 65-75 KIAS @ 3700 lb (Reduce 1 knot for each 80 lb Below 3700 lb) LANDING 1. Touchdown... SLIGHTLY TAIL LOW (Normal float landing attitude) 2. Control Wheel... HOLD FULL AFT THROUGH DECELERATION NOTE With forward loading, a slight nose-down pitch may occur if the elevator is not held full up as floatplane comes down off the step. BALKED LANDING 1. Throttle... FULL OPEN and 2700 RPM 2. Flap... 20 o 3. Climb Speed... 80 KIAS 4. Flaps... SLOWLY RETRACT to FLAPS UP AFTER LANDING 1. Water Rudders... DOWN (except on land) SECURING AIRPLANE 1. Fuel Selector Valve... OFF ISSUE 1 DOT APPROVED 19 OF 38
SUPPLEMENT M400-S08 FOUND AMPLIFIED NORMAL PROCEDURES TAXIING The water rudders should be in down position when taxiing. Engine speeds lower than 800 rpm should be used for normal taxi. Taxiing with higher RPM may result in engine overheating and the taxiing speed will not be appreciably increased. Also, higher taxiing speeds may cause excess water spray to strike the propeller tip and cause propeller tip erosion. During all low speed taxi operations, the elevator should be positioned to keep the bows of the floats out of the water as far as possible. Normally, this requires holding the elevator control full aft except when taxiing downwind in high wind conditions. For minimum taxi speed in close quarters, use idle RPM and a single magneto. This procedure is recommended for short periods of time only. Although taxiing is very simple with the water rudders, it is sometimes necessary to sail the floatplane under high wind condition. In addition to the normal flight controls, the wing flaps, ailerons and cabin doors will aid in sailing. Water rudders should be retracted during sailing. To taxi great distances, it may be advisable to taxi on the step with the water rudders retracted. Turns on the step from an upwind heading may be made with safety providing they are not too sharp and if ailerons are used to counteract any overturning / rolling tendency. CROSSWIND OPERATIONS In most floatplane operating areas, crosswind operating conditions are limited - either the water channel is narrow and the body of water is not greatly stirred up by winds or the body of water is large enough to allow pilots to minimize the crosswind and accept greater wave action. In higher winds where waves have been stirred up, spray may be developed during the early part of the takeoff run which is aggravated under increasing crosswinds. To minimize the adverse impact of spray on visibility and in extreme cases on engine operation, takeoffs should be made as nearly into the wind as possible. In extreme crosswind takeoff conditions the water rudders may need to be in the down position until the floatplane achieves adequate speed to make the rudder effective. 20 OF 38 ISSUE 1
FOUND SUPPLEMENT M400-S08 The flaps should not be deployed until the floatplane is established on the step. When planing on the step retract the water rudders, extend flaps as required and continue a normal takeoff. TAKEOFF Start the takeoff by applying full throttle smoothly while holding the control wheel full aft. When the nose stops rising, move the control wheel forward slowly to place the floats on the step. Slow control movement and light control pressures produce the best results. Attempts to force the floatplane into the planing attitude will generally result in loss of speed and delay in getting on the step. The floatplane will assume a planing attitude which permits acceleration to takeoff speed, at which time the floatplane will fly off smoothly. Takeoff flap between 10 o ~20 o can be used and 20 o is recommended throughout the takeoff run. When the airplane reaches a safe altitude and airspeed, retract the wing flaps slowly especially when flying over glassy water because a loss of altitude cannot be easily defined due to the loss of reference over glassy water. If porpoising is encountered while on the step, apply additional control wheel backpressure to correct the excessive nose-low attitude. If this does not correct the porpoising, immediately reduce power to idle and allow the floatplane to slow to taxi speed, at which time the takeoff can again be initiated. To clear an obstacle after takeoff with 20 degrees wing flap, use an obstacle clearance speed of 65 KIAS for maximum performance. Under some adverse combinations of higher takeoff weight, pressure altitude, and high air temperature or operation on glassy water, the airplane may require significantly longer takeoff distances to accelerate to the lift-off speed and extra takeoff distance should be allowed for these conditions. If lift-off is difficult due to high lake elevation or glassy water, the following procedure is recommended. With the floatplane in the planing attitude, apply full aileron as required to raise one float out of the water. When one float leaves the water, apply slight elevator backpressure to complete the takeoff. Care must be taken to stop the rising wing as soon as the float is clear of the water, and in crosswinds, raise only the downwind wing. With one float out of the water, the floatplane accelerates to takeoff speed much more rapidly. ISSUE 1 21 OF 38
SUPPLEMENT M400-S08 FOUND For a crosswind takeoff, start the takeoff with wing flaps up, ailerons deflected partially into the wind and water rudders extended for better directional control. Flaps should be extended to 20 degree and the water rudders retracted when the floatplane is on the step. The remainder of the takeoff is normal. If the floats are lifted from the water one at a time, the downwind float should be lifted first. LANDING To execute either a power on or a power off landing, approach at 80~90 KIAS with flaps up or 65~75 KIAS with flaps down. When landing in a restricted area use 30º flaps and an approach speed of 66 KIAS. GLASSY WATER LANDING Establish an elevation reference such as an island or shoreline adjacent to the landing area, extend flaps to 20º and use trim and power to establish a normal nose up landing attitude with a constant decent rate of 200 feet per minute and an approach speed of 66 KIAS. Fly the airplane onto the water maintaining constant speed and sink rates without attempting to flare, realizing that height above glassy water is impossible to judge. Once on the water reduce power to idle and slowly increase the back pressure on the yoke until the floatplane falls off the step. A glassy water landing requires a longer approach and longer total landing distance than a normal regular water landing. CROSSWIND LANDING The wing-low slip method should be used with the upwind float contacting the surface first while maintaining a slightly nose up normal float landing attitude. 22 OF 38 ISSUE 1
FOUND SUPPLEMENT M400-S08 SECTION 5 PERFORMANCE HEIGHT LOSS IN STALLS The height loss of up to 200 ft. may occur in stalls. ISSUE 1 23 OF 38
SUPPLEMENT M400-S08 FOUND AIRSPEED CALIBRATION The airspeed calibration is slightly changed due to the float installation and the weight increase from the landplane configuration. It is still acceptable to use the landplane airspeed calibration. 24 OF 38 ISSUE 1
FOUND SUPPLEMENT M400-S08 STALL SPEED AT 3700 POUNDS CONDITIONS POWER OFF MOST FORWARD CENTRE OF GRAVITY ANGLE OF BANK FLAP SETTING 0 o 30 o 45 o 60 o KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 54 60 58 64 64 71 76 85 10 51 58 55 62 61 69 72 82 15 48 55 52 59 57 65 68 77 20 46 53 49 57 55 63 65 75 30 44 51 47 55 52 61 62 72 NOTE: 1. Altitude loss during stall recovery may be upto 200 feet 2. Indicate speeds are approximate Figure 2 Stall Speeds ISSUE 1 25 OF 38
SUPPLEMENT M400-S08 FOUND BEST ANGLE-OF-CLIMB AT 3700 POUNDS CONDITIONS: Flaps Up 2600 RPM Full Throttle Mixture at Best Power Schedule PRESS ALT CLIMB SPEED BEST ANGLE OF CLIMB (deg) FEET KIAS -20 o C 0 o C 20 o C 40 o C S.L 65 6.9 6.2 5.5 4.8 2,000 67 6.0 5.3 4.6 4.0 4,000 68 4.7 4.1 3.5 3.0 6,000 70 3.5 3.0 2.4 2.0 8,000 70 2.5 2.0 1.5 1.0 10,000 71 1.5 1.0 0.5 0.1 Figure 3 Best Angle-of-Climb 26 OF 38 ISSUE 1
FOUND SUPPLEMENT M400-S08 BEST RATE-OF-CLIMB AT 3700 POUNDS CONDITIONS: Flaps Up 2600 RPM Full Throttle Mixture at Best Power Schedule PRESS ALT CLIMB SPEED RATE OF CLIMB (FPM) FEET KIAS -20 o C 0 o C 20 o C 40 o C S.L 79 830 770 707 644 2000 78 737 676 613 549 4000 76 604 543 480 417 6000 74 471 410 347 284 8000 73 339 277 214 151 10,000 72 209 146 - - - - - - Figure 4 Best Rate-of-Climb ISSUE 1 27 OF 38
SUPPLEMENT M400-S08 FOUND TIME, FUEL AND DISTANCE TO CLIMB AT 3700 POUNDS CONDITIONS: Flaps Up Full Throttle 2600 RPM Mixture at Best Power Schedule Standard Temperatures At Best Rate of Climb FROM SEA LEVEL PRESS TEMP CLIMB RATE OF TIME FUEL FUEL DIST ALT o C SPEED CLIMB IN USED USED IN FEET KIAS FPM MIN LITRES U.S GAL NM S.L 15 78 723 0 0 0.0 0 1000 13 78 700 1 2 0.5 2 2000 11 77 641 3 4 1.1 4 3000 9 76 581 5 7 1.7 6 4000 7 76 521 6 9 2.4 8 5000 5 75 460 8 12 3.1 11 6000 3 74 400 11 15 3.9 14 7000 1 74 340 13 18 4.8 18 8000-1 73 280 17 22 5.8 22 9000-3 72 220 21 27 7.1 28 10000-5 72 161 26 33 8.7 35 NOTES: 1. Add 7.5 litres (2 US gallons) of fuel for engine start, run-up, taxi and take off allowance. 2. Mixture leaned to climb schedule. 3. Increase time, fuel and distance by 10% for each 10 0 C above standard temperature. 4. Distances shown are based on zero wind. Figure 5 Time, Fuel and Distance to Climb 28 OF 38 ISSUE 1
FOUND SUPPLEMENT M400-S08 SECTION 6 WEIGHT AND BALANCE The Bush Hawk-XP equipped with Wipline floats must be loaded in accordance with the limitations in Section 2. These are shown as an aircraft weight/moment envelope or an aircraft weight versus c.g. locations chart on the following pages. WARNING IT IS THE RESPONSIBILITY OF THE AIRPLANE OWNER AND PILOT TO ENSURE THAT THE AIRPLANE IS LOADED PROPERLY. FLOAT BAGGAGE COMPARTMENTS Baggage may be carried in the float baggage compartments in accordance with the following limitations. Compartment Max. Weight Arm Moment/1000 LEFT 50 lbs -4 in. -0.2 RIGHT 50 lbs -4 in. -0.2 FLOATPLANE REFERENCE DATUM The floatplane reference datum for the purpose of weight and balance is the lower forward corner of the front doors. ISSUE 1 29 OF 38
SUPPLEMENT M400-S08 FOUND FLOATPLANE WEIGHING PROCEDURES 1. Preparation: a) De-fuel airplane. Refer to FAC2-M200 Maintenance Manual. b) Service engine oil as required to obtain a normal full indication. c) Move sliding seats to the most forward position. d) Raise flaps to the fully retracted position. e) Place all control surfaces in neutral position. f) Remove all non-required items from airplane. g) Remove the ventral fin from the tail wheel bracket. 2. Levelling: a) Jack up the tail wheel boom bracket on a stand such that the baggage compartment floor is near level longitudinally and laterally. Place a scale under this fitting. b) Drop plumb lines from both front door datum points. Mark the locations on the floor. Connect the points and extend the line out to the centre of both floats. c) Place scales under each float. The scales should be centred on the line described above. A minimum scale capacity of 1500 pounds is recommended for the main scales and 1000 pounds for the tail scale. 3. Weighing: a) With the airplane level and, record the weight shown on each scale. Deduct the tare, if any, from each reading. 4. Measuring Arms: a) Obtain measurement A by measuring horizontally (along the floor) from the floatplane reference datum line previously drawn on the floor (Item 2b) to a point on the floor directly below the tail wheel boom bracket. See the illustration below. 5. Calculate CG and Weight: a) Using weights from Item 3 and measurements from Item 4, the airplane Basic Empty Weight and C.G. can be determined by completing the following table. b) DO NOT forget to add in the contribution from the ventral fin. The weight and arm of the ventral fin can be found in the Equipment List provided at the time of delivery of the aircraft. 30 OF 38 ISSUE 1
FOUND SUPPLEMENT M400-S08 ISSUE 1 31 OF 38
SUPPLEMENT M400-S08 FOUND Weighing Tare Scale Net Arm Moment Point Reading Weight (lbs) (lbs) (lbs) (inches) (in-lbs) Tail A = R Main (Float) 0.0 L Main (Float) 0.0 Ventral Fin* --- --- 3.0 190.0 570.0 Total (Weighed) CG= CG = Total Moment / Total Net Weight Use spaces below to add or subtract items from weighed condition. Empty Weight Drainable Unusable Fuel (6 lbs/usg), 1.7 USG Basic Empty Weight CG= 10.2 21.8 222.4 Net Weight = Scale Reading - Tare Moment = Net Weight * Arm Arm is measured from the aircraft datum (front door forward lower corner). * - These are nominal figures for the Ventral Fin. The actual weight and arm should be used instead of the nominal numbers shown above if available. These figures are supplied with the aircraft at the time of delivery. 32 OF 38 ISSUE 1
FOUND SUPPLEMENT M400-S08 FLOATPLANE WEIGHT AND BALANCE PROCEDURES The following information will enable you to operate your within the prescribed weight and centre of gravity limitations. To figure weight and balance, use the Sample Loading Problem, Loading Graph (in Section 6 of M400), and Centre of Gravity Moment Envelopes as follows: 1. Take the Basic Empty Weight and Moment from appropriate weight and balance records carried in your airplane and enter them in the column titled YOUR AIRPLANE on the Sample Loading Problem. NOTE In addition to the Basic Empty Weight and Moment noted on these records, the C.G. arm (fuselage station) is also shown, but need not be used on the Sample Loading Problem. The moment which is shown must be divided by 1000 and this value used as the moment/1000 on the loading problem. 2. Use the Loading Graph to determine the moment/1000 for each additional item to be carried; then list these on the loading problem. NOTE Loading Graph information for the pilot, passengers and baggage is based on seats positioned for average occupants and baggage loaded in the centre of the aft baggage compartment as shown on the Loading Arrangements diagram. For loadings which may differ from these, the Sample Loading Problem lists fuselage stations for these items to indicate their forward and aft C.G. range limitations (seat travel and baggage compartment limitation). Additional moment calculations, based on the actual weight and C.G. arm (fuselage station) of the item being loaded, must be made if the position of the load is different from that shown on the Loading Graph. 3. Total the weights and moments/1000 and plot these values on the centre of Gravity Moment Envelope to determine whether the point falls within the envelope, and if the loading is acceptable. ISSUE 1 33 OF 38
SUPPLEMENT M400-S08 FOUND SAMPLE LOADING PROBLEM FOR FLOATPLANE 1. Basic Empty Weight (Use the data pertaining to your airplane as it is presently equipped. Includes unusable fuel and full oil). 2. Usable Fuel (At 6.0 lbs/usg) 98 USG Maximum 60 USG (used for example) 3. Pilot and Front Passenger (Station 17.8 & 200 pounds each) 4. Rear Passenger (Station 55.0 & 200 pounds each) 5. Main Baggage Area (Station 76 to 114; 250 pounds. max. @ Station 94) 6. Ramp Weight and Moment (add columns) 7. Fuel Allowance for Engine Start, Taxi and Run-Up 8. Takeoff Weight and Moment (Subtract Step 7 from Step 6) WEIGHT AND MOMENT TABULATION SAMPLE AIRPLANE WEIGHT MOMENT ARM WEIGHT MOMENT (lbs) (lb-in /1000) (in) 2360 36.7 15.6 360 7.8 21.8 400 7.1 17.8 400 22.0 55.0 50 4.7 94.0 3570 78.4-7 -0.2 21.8 3563 78.3 22.0 YOUR AIRPLANE (lbs) (lb-in /1000) 9. Locate this point (3563 at 78.3) on the Centre of Gravity Moment Envelope, and since this point falls within the envelope, the loading is acceptable. 34 OF 38 ISSUE 1
FOUND SUPPLEMENT M400-S08 CENTER OF GRAVITY MOMENT ENVENLOPE 3800 3600 LOADED AIRPLANE WEIGHT (LB) 3400 3200 3000 2800 2600 2400 2200 0 20 40 60 80 100 LOADED AIRPLANE MOMENT/1000 (POUND-INCHES) Figure 6 Loaded Airplane Moment/1000 (pound-inches) ISSUE 1 35 OF 38
SUPPLEMENT M400-S08 FOUND CENTER OF GRAVITY RANGE ENVENLOPE 3800 3600 LOADED AIRPLANE WEIGHT (LB) 3400 3200 3000 2800 2600 2400 2200 16 17 18 19 20 21 22 23 24 25 AIRPLANE C.G. LOCATION (IN. AOD) Figure 7 Airplane CG Location (Inches AFT of Datum) 36 OF 38 ISSUE 1
FOUND SUPPLEMENT M400-S08 SECTION 7 AIRPLANE AND SYSTEMS DESCRIPTION In addition to the Wipline Model 3450 floats installation, the aircraft must incorporate the Found Aircraft Canada Inc. approved floatplane kit. With either of these installations, the floatplane is identical to the landplane with the following exceptions: FOUND AIRCRAFT CANADA MODIFICATIONS 1. Floats, incorporating water rudder steering system. 2. Water rudder steering cables for retraction and steering control of the water rudders. 3. A water rudder retraction lever connected to the dual water rudders by cables is located on the cabin floor between the front seats. 4. Ventral fin located on the bottom of the fuselage and the finlets on the top of the stabilizer. 5. Loading steps, which are mounted to the float struts. 6. Floatplane placards. WATER RUDDER SYSTEM Retractable water rudders, mounted at the aft end of each float, are connected by a system of cables and springs to the rudder pedals. Normal rudder pedal operation moves the water rudders to provide steering control for taxiing. A water rudder retraction lever, located on the cabin floor between the front seats, is used to manually raise and lower the water rudders. The handle should be in the UP (aft) position during takeoff, landing, and in flight. With the handle in this position, the water rudders are up. When the lever is rotated forward to the DOWN position, the water rudders extend to the full down position for water taxiing. ISSUE 1 37 OF 38
SUPPLEMENT M400-S08 FOUND UP DOWN UP DOWN Figure 8 Water Rudder Retraction System 38 OF 38 ISSUE 1